Aircraft turbine engine with at least two bodies and means for drawing power

Abstract

An aircraft turbine engine includes a low-pressure body and a high-pressure body, as well as means for drawing power on said low-pressure body, said means having a first shaft for drawing power, the radially inner end of said first shaft bearing a first bevel gear meshed with a first idler bevel wheel driven by the low-pressure body, the turbine engine further having a first annular bearing support which extends about an axis and is rigidly connected to a stator. The first bearing support includes a first cylindrical portion which extends coaxially with a second substantially cylindrical portion of the idler wheel, said first and second portions being guided one inside the other by bearings, and the idler wheel is driven by the low-pressure body by means of an annular damping piece which is independent of the first bearing support.

The invention claimed is: 
     
       1. An aircraft turbine engine, comprising a low-pressure body and a high-pressure body, as well as drawing means for drawing power on at least said low-pressure body, said drawing means comprising a first power drawing shaft extending radially with respect to a longitudinal axis (A) of rotation of said low-pressure and high pressure bodies, the first power drawing shaft comprising a radially inner end carrying a first bevel gear meshed with a first idler bevel wheel driven by said low-pressure body, the aircraft turbine engine further comprising a first annular bearing support extending around said axis and integral with a stator,
 wherein said first bearing support comprises a first cylindrical portion which extends coaxially with a second cylindrical portion of said idler bevel wheel, these first and second cylindrical portions being guided one inside the other by bearings, and said idler bevel wheel is driven by said low-pressure body through an annular damping part which is independent of said first bearing support. 
 
     
     
       2. The aircraft turbine engine according to  claim 1 , wherein said first and second cylindrical portions are guided by two adjacent bearings axially spaced from each other. 
     
     
       3. The aircraft turbine engine according to  claim 1 , wherein said first bearing support is connected to a housing for guiding said first power drawing shaft. 
     
     
       4. The aircraft turbine engine according to  claim 1 , wherein said first bearing support has in axial half-section an L-shape which radially inner periphery comprises said first cylindrical portion and is configured to be surrounded at least in part by said idler bevel wheel. 
     
     
       5. The aircraft turbine engine according to  claim 1 , wherein said idler bevel wheel has in axial half-section an L-shape, which radially inner periphery comprises said second cylindrical portion and is configured to be surrounded at least in part by said bearing support. 
     
     
       6. The aircraft turbine engine according to  claim 1 , wherein said idler bevel wheel is driven by said low-pressure body via the annular damping part having a capacity for elastic deformation in torsion about at least one of said axis (A) or in a radial direction. 
     
     
       7. The aircraft turbine engine according to  claim 1 , wherein said idler bevel wheel is driven by said low-pressure body via the annular damping part having at least one of an annular row of through orifices or an annular portion with a C-shaped axial half-section, an opening of which is oriented axially upstream or downstream. 
     
     
       8. The aircraft turbine engine according to  claim 1 , wherein said first bevel gear and said first idler bevel wheel are housed in a lubrication enclosure configured for lubricating a bearing for guiding the high-pressure body. 
     
     
       9. The aircraft turbine engine according to  claim 8 , further comprising high pressure drawing means for drawing power on said high-pressure body, the high pressure drawing means comprising a second power drawing shaft extending radially with respect to said axis (A) and comprising a radially inner end carrying a second bevel gear meshing with a second idler bevel wheel driven by said high-pressure body, said second bevel gear and said second idler bevel wheel being housed in said lubrication enclosure. 
     
     
       10. The aircraft turbine engine according to  claim 9 , further comprising an intermediate casing comprising an annular shroud around which is arranged an annular row of tubular arms, the annular shroud separating said lubrication enclosure from an annular gas flow duct extending around the lubrication enclosure, and extending axially between said first bearing support and said bearing for guiding the high-pressure body, said first and second power drawing shafts extending through different arms of the intermediate casing. 
     
     
       11. A method of modular assembly of the aircraft turbine engine according to  claim 10 , comprising:
 (a) assembling a first module of the aircraft turbine engine, the first module comprising a part of the high-pressure body, at least a part of the intermediate casing, a first part of the low-pressure body including a main shaft, and the second power drawing means; 
 (b) mounting a second turbine engine module and assembling it by axial translation from upstream on and around a part of said first module, the second module comprising said first bearing support and said first power drawing means; and 
 (c) mounting a third turbine engine module and assembling it by axial translation from upstream, the third module comprising a second part of the low-pressure body including a secondary shaft, as well as said damping part, the third turbine engine module comprising a part engaged radially between parts of said first and second modules and enabling to engage the main and secondary shafts of the low-pressure body via first splines, and, the damping part carried by said secondary shaft with said idler bevel wheel or an intermediate part already engaged with this idler wheel via second splines.